FR3125176B1 - Electrical architecture for aircraft - Google Patents

Electrical architecture for aircraft Download PDF

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Publication number
FR3125176B1
FR3125176B1 FR2107430A FR2107430A FR3125176B1 FR 3125176 B1 FR3125176 B1 FR 3125176B1 FR 2107430 A FR2107430 A FR 2107430A FR 2107430 A FR2107430 A FR 2107430A FR 3125176 B1 FR3125176 B1 FR 3125176B1
Authority
FR
France
Prior art keywords
distribution network
electrical distribution
inverter
distributing
aircraft
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
FR2107430A
Other languages
French (fr)
Other versions
FR3125176A1 (en
Inventor
Philippe Naneix
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Electrical and Power SAS
Original Assignee
Safran Electrical and Power SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Safran Electrical and Power SAS filed Critical Safran Electrical and Power SAS
Priority to FR2107430A priority Critical patent/FR3125176B1/en
Priority to EP22744254.8A priority patent/EP4367773A1/en
Priority to US18/576,725 priority patent/US20240291280A1/en
Priority to PCT/FR2022/051202 priority patent/WO2023281179A1/en
Priority to CN202280047737.1A priority patent/CN117597847A/en
Publication of FR3125176A1 publication Critical patent/FR3125176A1/en
Application granted granted Critical
Publication of FR3125176B1 publication Critical patent/FR3125176B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J4/00—Circuit arrangements for mains or distribution networks not specified as ac or dc
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J3/00—Circuit arrangements for ac mains or ac distribution networks
    • H02J3/38—Arrangements for parallely feeding a single network by two or more generators, converters or transformers
    • H02J3/381—Dispersed generators
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J3/00—Circuit arrangements for ac mains or ac distribution networks
    • H02J3/38—Arrangements for parallely feeding a single network by two or more generators, converters or transformers
    • H02J3/40—Synchronising a generator for connection to a network or to another generator
    • H02J3/42—Synchronising a generator for connection to a network or to another generator with automatic parallel connection when synchronisation is achieved
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02M—APPARATUS FOR CONVERSION BETWEEN AC AND AC, BETWEEN AC AND DC, OR BETWEEN DC AND DC, AND FOR USE WITH MAINS OR SIMILAR POWER SUPPLY SYSTEMS; CONVERSION OF DC OR AC INPUT POWER INTO SURGE OUTPUT POWER; CONTROL OR REGULATION THEREOF
    • H02M7/00—Conversion of ac power input into dc power output; Conversion of dc power input into ac power output
    • H02M7/66—Conversion of ac power input into dc power output; Conversion of dc power input into ac power output with possibility of reversal
    • H02M7/68—Conversion of ac power input into dc power output; Conversion of dc power input into ac power output with possibility of reversal by static converters
    • H02M7/72—Conversion of ac power input into dc power output; Conversion of dc power input into ac power output with possibility of reversal by static converters using discharge tubes with control electrode or semiconductor devices with control electrode
    • H02M7/79—Conversion of ac power input into dc power output; Conversion of dc power input into ac power output with possibility of reversal by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal
    • H02M7/797—Conversion of ac power input into dc power output; Conversion of dc power input into ac power output with possibility of reversal by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D2221/00—Electric power distribution systems onboard aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D41/00—Power installations for auxiliary purposes
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J2310/00—The network for supplying or distributing electric power characterised by its spatial reach or by the load
    • H02J2310/40—The network being an on-board power network, i.e. within a vehicle
    • H02J2310/44—The network being an on-board power network, i.e. within a vehicle for aircrafts
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J9/00—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting
    • H02J9/04—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source
    • H02J9/06—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source with automatic change-over, e.g. UPS systems
    • H02J9/062—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source with automatic change-over, e.g. UPS systems for AC powered loads

Landscapes

  • Engineering & Computer Science (AREA)
  • Power Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Inverter Devices (AREA)
  • Direct Current Feeding And Distribution (AREA)
  • Supply And Distribution Of Alternating Current (AREA)

Abstract

L’invention concerne une architecture électrique (2) pour aéronef comprenant :- un premier réseau (16) de distribution électrique propulsif distribuant une haute tension continue, - un deuxième réseau (18) de distribution électrique propulsif distribuant une haute tension continue, - un premier réseau (46) de distribution électrique alternatif distribuant une tension alternative triphasée, - un deuxième réseau (54) de distribution électrique alternatif distribuant une tension alternative triphasée,- un premier onduleur (44) connecté entre le premier réseau de distribution électrique propulsif et le premier réseau de distribution électrique alternatif, - un deuxième onduleur (52) connecté entre le deuxième réseau de distribution électrique propulsif et le deuxième réseau de distribution électrique alternatif, - un boitier électronique (60) connecté au premier onduleur et au deuxième onduleur pour commander la fréquence de la tension alternative triphasée générée par le premier onduleur et la fréquence de la tension alternative triphasée générée par le deuxième onduleur. Figure à publier avec l’abrégé : Figure 1The invention relates to an electrical architecture (2) for an aircraft comprising: - a first propulsion electrical distribution network (16) distributing a high DC voltage, - a second propulsion electrical distribution network (18) distributing a high DC voltage, - a first alternating electrical distribution network (46) distributing a three-phase alternating voltage, - a second alternating electrical distribution network (54) distributing a three-phase alternating voltage, - a first inverter (44) connected between the first propulsion electrical distribution network and the first alternating electrical distribution network, - a second inverter (52) connected between the second propulsion electrical distribution network and the second alternating electrical distribution network, - an electronic box (60) connected to the first inverter and to the second inverter to control the frequency of the three-phase alternating voltage generated by the first inverter and the frequency of the three-phase alternating voltage generated by the second inverter. Figure to be published with the abstract: Figure 1

FR2107430A 2021-07-08 2021-07-08 Electrical architecture for aircraft Active FR3125176B1 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
FR2107430A FR3125176B1 (en) 2021-07-08 2021-07-08 Electrical architecture for aircraft
EP22744254.8A EP4367773A1 (en) 2021-07-08 2022-06-21 Electrical architecture for an aircraft
US18/576,725 US20240291280A1 (en) 2021-07-08 2022-06-21 Electrical architecture for an aircraft
PCT/FR2022/051202 WO2023281179A1 (en) 2021-07-08 2022-06-21 Electrical architecture for an aircraft
CN202280047737.1A CN117597847A (en) 2021-07-08 2022-06-21 Electrical architecture for an aircraft

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2107430A FR3125176B1 (en) 2021-07-08 2021-07-08 Electrical architecture for aircraft
FR2107430 2021-07-08

Publications (2)

Publication Number Publication Date
FR3125176A1 FR3125176A1 (en) 2023-01-13
FR3125176B1 true FR3125176B1 (en) 2023-11-17

Family

ID=77226938

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2107430A Active FR3125176B1 (en) 2021-07-08 2021-07-08 Electrical architecture for aircraft

Country Status (5)

Country Link
US (1) US20240291280A1 (en)
EP (1) EP4367773A1 (en)
CN (1) CN117597847A (en)
FR (1) FR3125176B1 (en)
WO (1) WO2023281179A1 (en)

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2758782B2 (en) * 1992-05-22 1998-05-28 三菱電機株式会社 Power supply
US6806589B1 (en) * 2003-07-21 2004-10-19 Hamilton Sundstrand Corporation No break electric power transfer system
US7612514B2 (en) * 2006-11-09 2009-11-03 Honeywell International Inc. Architecture and a multiple function power converter for aircraft
FR2963499B1 (en) * 2010-07-28 2013-07-12 Airbus Operations Sas ELECTRICAL POWER SYSTEM OF AN AIRCRAFT
US10934935B2 (en) * 2017-01-30 2021-03-02 Ge Aviation Systems Llc Engine core assistance
US11133780B2 (en) * 2019-06-05 2021-09-28 The Boeing Company Non-break power transfer for variable frequency generators
GB2587667A (en) * 2019-09-06 2021-04-07 Rolls Royce Plc Electrical power distribution
FR3103647B1 (en) * 2019-11-21 2021-10-22 Safran ELECTRICAL ARCHITECTURE FOR A THERMAL / ELECTRIC HYBRID PROPULSION AIRCRAFT AND TWIN-ENGINE AIRCRAFT INCLUDING SUCH ARCHITECTURE

Also Published As

Publication number Publication date
US20240291280A1 (en) 2024-08-29
WO2023281179A1 (en) 2023-01-12
FR3125176A1 (en) 2023-01-13
CN117597847A (en) 2024-02-23
EP4367773A1 (en) 2024-05-15

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